Variable structure control for satellite attitude stabilization in elliptic orbits using solar radiation pressure

Patel, Tejashkumar R.; Kumar, Krishna Dev; Behdinan, Kamran

doi:10.1016/j.actaastro.2008.08.003

Cited by 24 publications

(21 citation statements)

References 32 publications

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“…In the closed-loop system, certain related error signals converge to zero in finite time, and the pitch angle trajectory tracking error converges to zero exponentially. Unlike the VSC laws [18,19], the adaptive VSC law [20], and the adaptive laws [23], the VS-MRAC law in this paper does not require feedback of the second derivative of the pitch angle. Simulation results are presented which show that the VS-MRAC law accomplishes precise large pitch angle control of the satellite, despite unmodelled dynamics, parameter uncertainty and external disturbance moment.…”

Section: Introductionmentioning

confidence: 88%

“…The region in which BB T inverse exists has been determined [16,19]. Indeed the simulation results presented in the next section show that the control system is well defined in the region of interest and the attitude control can be precisely accomplished.…”

Section: Vs-mrac System For Pitch Controlmentioning

confidence: 95%

“…The variable structure control (VSC) of satellites with uncertainties has been treated using the SRP [18,19]. The VSC law [18] is developed using linear switching function, but the terminal sliding mode controller of [19] uses a nonlinear switching function. The switching gains are designed based on the bounds on the uncertain functions in the model.…”

Section: Introductionmentioning

confidence: 99%

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Solar Pressure Variable Structure Model Reference Adaptive Spacecraft Attitude Control in Elliptic Orbits

Lee

Singh

2015

AIAA Guidance, Navigation, and Control Conference

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Based on the variable structure model reference adaptive control (VS-MRAC) theory, a new adaptive control system for the attitude control of satellites in elliptic orbits with uncertain dynamics, using solar radiation pressure (SRP), is derived. The nonaffine-incontrol nonlinear spacecraft model includes the gravity gradient torque, the control torque produced by two solar flaps, and external time-varying disturbance torque. The objective here is to derive a control law for the pitch attitude control using the pitch angle and pitch rate feedback. For the trajectory tracking of the pitch angle, a variable structure model reference adaptive attitude control system, including two relays and linear filters, is designed. Although, the modulation functions of the relays are functions of certain auxiliary signals, for simplicity in implementation, these functions are assigned constant values. Simulation results are presented which show that the simplified VS-MRAC law accomplishes precise attitude control of the spacecraft, despite unmodelled (unstructured) nonlinearities, parameter uncertainty and external disturbance torque in the model. NomenclatureA c , B c , h c , g g = Closed-loop system matrices a, e = Semi-major axis and eccentricity a mi , k m = Parameters of reference model S m B = Control input matrix A s , l p = Control surface area and the moment arm C s , C s = Solar parameter e 0 , e 0 , e 1 = Error signals f 0 , f 1 = Modulation functions g 0 , g a , g = Nonlinear functions I x , I y , I z = Moments of inertia of the satellite K = (I x − I y )/I z M g = Gravity gradient torque, M s , M d = Solar torque and disturbance torque i = Inclination of the orbital plane with ecliptic plane p = Solar radiation pressure, 4.65 × 10 −6 N m −2 y p , y m = Output signals * Professor, AIAA SciTech s = Laplace variable or differential operator v 0 , v 1 , v = Control input signals X b , Y b , Z b = Principal axes of the satellite α, α r = Pitch angle, reference pitch anglẽ α = Tracking error ξ i , χ i = Auxiliary signals X o , Y o , Z o = Orbital coordinates with X o along the local vertical, X o Y o defining the orbital plane δ i (i = 1, 2) = Control plate rotations θ = Orbital angle λ = Pitch attitude angle of the satellite with respect to orbital coordinates Λ f , λ i , b f = Regressor filter parameters ρ s = Reflectivity of the control surfaces φ = Location of the Sun from the line of nodes Ω = Mean orbital rate ω 1 , ω 2 , ω a = Regressor vectors θ i , Θ a , θ * i = Controller gains

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Section: Introductionmentioning

confidence: 88%

Section: Vs-mrac System For Pitch Controlmentioning

confidence: 95%

Section: Introductionmentioning

confidence: 99%

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Solar Pressure Variable Structure Model Reference Adaptive Spacecraft Attitude Control in Elliptic Orbits

Lee

Singh

2015

AIAA Guidance, Navigation, and Control Conference

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“…Simulation results curves are from Fig.1 to Fig.4 by Matlab procedures. We compare VSC based on the reaching law (10) to VSC based on the reaching law (7) through some simulations. The simulation results indicate that the VSC based on the reaching law (10) has smaller chattering and its stability is prior to the later.…”

Section: S K Qt S K Qt T S K Qt Cg K Cg Kmentioning

confidence: 99%

“…The intelligent control strategies such as adaptive control [8] and fuzzy control [9] are applied to the design of Manuscript VSC system. Meanwhile, VSC is widely applied in satellite attitude control [10], dynamic economic system [11] and other practical systems. The reaching law method is a common method for VSC.…”

Section: Introductionmentioning

confidence: 99%

Variable structure control for discrete-time singular system based on reaching law with dynamic disturbance compensator

Liu

Gao

Wang

et al. 2011

2011 Chinese Control and Decision Conference (CCDC)

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Synthesis problem of variable structure control (VSC) for discrete-time singular system (DSS) with internal parameter perturbation and external disturbance is considered in this paper. The dynamic switching function which is used to guarantee the stability of the control system in the switching band is provided. The discrete singular reaching law with dynamic disturbance compensator is designed to eliminate the restriction of the system uncertainties is bounded and the satisfaction of matching conditions compared with conventional VSC. Essential condition of sliding mode which can cross the switching plane step by step is considered. The discrete singular variable structure controller is designed by applying the reaching law, which can guarantee the system to reach the switching plane in finite time, decrease the system chattering effectively and enhance the dynamic quality of the control system. Simulation results illustrate the feasibility and validity of the proposed approach.

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Robust Output Feedback Attitude Control of Spacecraft Using Solar Radiation Pressure

Srinivasan

Lee

Singh

2015

Progress in Systems Engineering

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Variable structure control for satellite attitude stabilization in elliptic orbits using solar radiation pressure

Cited by 24 publications

References 32 publications

Solar Pressure Variable Structure Model Reference Adaptive Spacecraft Attitude Control in Elliptic Orbits

Solar Pressure Variable Structure Model Reference Adaptive Spacecraft Attitude Control in Elliptic Orbits

Variable structure control for discrete-time singular system based on reaching law with dynamic disturbance compensator

Robust Output Feedback Attitude Control of Spacecraft Using Solar Radiation Pressure

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